Similarly shaped airfoils to NACA65-610 a=0.6
New! Bulk download of polars in Excel format: NACA65-610%20a%3D0.6.xlsx
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (0) | Similarly shaped airfoils
Plain Flapped Shapes: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Basic Data: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl | Curve fits | Lift curve slopes
Data source comparison (Codes, CFD, Wind tunnel)
Compressibility Effects: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl
Roughness Effects: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl
Plain Flap Effects: cl,max vs flap deflection: all flap chords | 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cl vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cm vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cd vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
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2. NACA64-610 a=0.6
3. GA 40A610
4. GA 40-610
5. GA 37A610
6. NACA64-610 a=0.5
7. NACA63-610 a=0.6
8. GA 35A610
9. NACA66-610 a=0.6
10. GA 37-610
11. NACA65-611 a=0.6
12. NACA65-609 a=0.6
13. NACA63-610 a=0.5
14. NACA64-611 a=0.6
15. NACA65-610 a=0.8
16. NACA66-609 a=0.6
17. NACA66-610 a=0.5
18. NACA65-609 a=0.5
19. GA 40-611
20. NACA65-611 a=0.5
21. GA 40A611